US7510390B2 - Machinable composite mold - Google Patents

Machinable composite mold Download PDF

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Publication number
US7510390B2
US7510390B2 US11/180,831 US18083105A US7510390B2 US 7510390 B2 US7510390 B2 US 7510390B2 US 18083105 A US18083105 A US 18083105A US 7510390 B2 US7510390 B2 US 7510390B2
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Prior art keywords
mold
composite structure
making
structure according
fibers
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US11/180,831
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US20070012858A1 (en
Inventor
Richard A. Callis
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Hexcel Corp
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Hexcel Corp
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Priority to US11/180,831 priority Critical patent/US7510390B2/en
Assigned to HEXCEL CORPORATION reassignment HEXCEL CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: CALLIS, RICHARD A.
Assigned to DEUTSCHE BANK TRUST COMPANY AMERICAS, AS ADMINISTRATIVE AGENT reassignment DEUTSCHE BANK TRUST COMPANY AMERICAS, AS ADMINISTRATIVE AGENT GRANT OF PATENT SECURITY INTEREST (IP SUPPLEMENT NO. 2) Assignors: HEXCEL CORPORATION
Assigned to HEXCEL CORPORATION reassignment HEXCEL CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: CALLIS, RICHARD A.
Priority to CN2013101996551A priority patent/CN103286889A/zh
Priority to PCT/US2006/027001 priority patent/WO2007008953A2/en
Priority to EP14160351.4A priority patent/EP2746023B1/de
Priority to CN2006800255184A priority patent/CN101258012B/zh
Priority to ES14160351.4T priority patent/ES2573496T3/es
Priority to ES06786977.6T priority patent/ES2471121T3/es
Priority to EP20060786977 priority patent/EP1915245B1/de
Publication of US20070012858A1 publication Critical patent/US20070012858A1/en
Priority to US12/400,017 priority patent/US7695661B2/en
Publication of US7510390B2 publication Critical patent/US7510390B2/en
Application granted granted Critical
Assigned to DEUTSCHE BANK TRUST COMPANY AMERICAS, AS ADMINISTRATIVE AGENT reassignment DEUTSCHE BANK TRUST COMPANY AMERICAS, AS ADMINISTRATIVE AGENT GRANT OF PATENT SECURITY INTEREST Assignors: HEXCEL CORPORATION
Assigned to HEXCEL CORPORATION, HEXCEL REINFORCEMENTS CORP. reassignment HEXCEL CORPORATION RELEASE OF PATENT SECURITY INTEREST Assignors: DEUTSCHE BANK TRUST COMPANY AMERICAS, AS ADMINISTRATIVE AGENT
Priority to US12/726,677 priority patent/US7972548B2/en
Assigned to BANK OF AMERICA, N.A. reassignment BANK OF AMERICA, N.A. SECURITY AGREEMENT Assignors: HEXCEL CORPORATION
Assigned to HEXCEL CORPORATION reassignment HEXCEL CORPORATION RELEASE BY SECURED PARTY (SEE DOCUMENT FOR DETAILS). Assignors: DEUTSCHE BANK TRUST COMPANY AMERICAS
Priority to US13/118,520 priority patent/US8257631B2/en
Assigned to RBS CITIZENS, N.A., AS ADMINISTRATIVE AGENT reassignment RBS CITIZENS, N.A., AS ADMINISTRATIVE AGENT SECURITY AGREEMENT Assignors: HEXCEL CORPORATION, HEXCEL HOLDINGS LUXEMBOURG S.A.R.L.
Assigned to HEXCEL CORPORATION reassignment HEXCEL CORPORATION RELEASE BY SECURED PARTY (SEE DOCUMENT FOR DETAILS). Assignors: BANK OF AMERICA, N.A.
Assigned to HEXCEL CORPORATION reassignment HEXCEL CORPORATION TERMINATION OF SECURITY INTEREST IN PATENTS Assignors: CITIZENS BANK, NATIONAL ASSOCIATION (F/K/A RBS CITIZENS, N.A.)
Assigned to HEXCEL HOLDINGS LUXEMBOURG S.À.R.L., HEXCEL CORPORATION reassignment HEXCEL HOLDINGS LUXEMBOURG S.À.R.L. RELEASE BY SECURED PARTY (SEE DOCUMENT FOR DETAILS). Assignors: CITIZENS BANK, NATIONAL ASSOCIATION
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
    • B29C33/3842—Manufacturing moulds, e.g. shaping the mould surface by machining
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
    • B29C33/3842—Manufacturing moulds, e.g. shaping the mould surface by machining
    • B29C33/3857—Manufacturing moulds, e.g. shaping the mould surface by machining by making impressions of one or more parts of models, e.g. shaped articles and including possible subsequent assembly of the parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B29K2105/12—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts of short lengths, e.g. chopped filaments, staple fibres or bristles
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/31504—Composite [nonstructural laminate]
    • Y10T428/31721—Of polyimide

Definitions

  • Bismaleimide and polyimide resins have been used widely in combination with carbon fibers as the materials of choice for composite molds.
  • Woven carbon fabric that has been hand cut into square pieces is applied to the master mold to form multiple individual layers.
  • the pieces of woven fabric are oriented in the master mold to provide smooth tooling surfaces.
  • Resin can be introduced into the woven fiber pieces in a number of ways. For example, the resin can be added through automated impregnation by the material manufacturer (prepreg). Alternatively, the resin can be introduced into the woven pieces when they are in the master mold. This is accomplished by vacuum infusion or simple hand application of the resin.
  • molds are provided for use in making composite structures wherein the mold body is made from a quasi-isotropic material that is composed of a plurality of randomly oriented fiber bundles impregnated with a resin. It was discovered that the use of randomly oriented fiber bundles or chips, which are impregnated with an appropriate resin, provides a composite mold that can be machined to the same surface tolerances as metal molds.
  • the mold body includes at least two mold layers wherein both of the mold layers have a surface that forms at least a part of the tool surface.
  • the tool surfaces on the two or more mold layers are formed using a master mold and then they are further shaped, if desired, by machining.
  • the present invention covers methods for molding composite structures using the composite molds as described above.
  • the present invention covers methods for modifying the composite molds. These methods involve modifying the pre-existing molds by machining the mold and/or by bonding at least one additional mold layer to the tool surface. The additional layer is then machined, if desired, to form a modified tool surface. This type of mold modification method is useful in changing the surface configuration of the mold or repairing a damaged tool surface.
  • FIG. 2 is a diagrammatic representation of a portion of a mold in accordance with the present invention where the mold shown in FIG. 1 has been machined to form a different tool surface.
  • FIG. 4A is a partial view of an exemplary mold in accordance with the present invention prior to machining and FIG. 4B is the same mold after it has been machined.
  • FIG. 1 A portion of an exemplary composite mold in accordance with the present invention is shown diagrammatically at 10 in FIG. 1 .
  • the mold is intended for use in fabricating composite parts in accordance with known autoclave curing processes where service temperatures are typically between 350° F. and 500° F. However, if desired, the mold may be used in other molding processes where it is not necessary to heat the material being molded.
  • the mold 10 is designed as a replacement for existing composite molds or tooling that are typically supported by another structure during the molding process. These types of composite molds have been in use for many years to mold a wide variety of composite materials.
  • the molds of the present invention may be used in any situation where such a composite mold is required.
  • the mold 10 includes a mold body 11 that has tool surfaces 12 and 13 that are shaped to provide the desired molded surface on the composite structure that is being fabricated.
  • the tool surfaces 12 and 13 are shaped using a master mold (shown in phantom at 14 ) in accordance with well-known procedures for making composite molds.
  • the mold body 11 is shown having six mold layers 16 , 18 , 20 , 22 , 24 and 26 .
  • the mold layers are formed in accordance with conventional lay up procedures where each uncured layer is sequentially applied to the master mold 14 beginning with mold layer 26 and ending with mold layer 16 . After the desired numbers of layers are applied, the resulting body is cured to form the mold body 11 .
  • the tool surface 12 is formed by a single mold layer 26 . This is to be contrasted with tool surface 13 that is formed by mold layers 26 , 24 and 22 .
  • each of the mold layers used in the mold body be made from quasi-isotropic material that is composed of randomly oriented fiber bundles or chips that are impregnated with a suitable resin. It is only necessary that the mold layers that form the tool surfaces (either by initial molding or subsequent machining) be made from semi-isotropic material.
  • the term “quasi-isotropic material”, as used herein, also covers those composite materials referred to as “transversely-isotropic”. These materials are made up of randomly oriented chips or bundles, which are composed of fibers that are impregnated with a suitable resin. Exemplary quasi-isotropic materials are described in European Patent No. EP 1,134,314 B1.
  • the quasi-isotropic materials that may be used to make composite molds in accordance with the present invention include randomly oriented chip or bundles of carbon fiber impregnated with a suitable resin.
  • Other types of fibers such as glass fibers, ceramic fibers and hybrids may be used, if desired.
  • the fibers are grouped together to form a rectangular chip or bundle.
  • the chips should be from 1 ⁇ 2 to 4 inches long and from 1 ⁇ 8 to 1 inch wide.
  • the fibers in each chip may be unidirectional or woven. Chips with unidirectional fibers are preferred.
  • Each of the chips should contain from 1,000 to 100,000 fibers.
  • the chips may contain differing amounts of resin and fibers. It is preferred that the resin content be from 30 to 50 volume percent with 36 to 40 volume percent being particularly preferred resin.
  • the quasi-isotropic material is preferably provided as a sheet or layer of chips that forms an uncured prepreg that is from 0.04 to 0.5 inch thick.
  • the preferred thickness of the layer of chips is from 0.06 to 0.10 inch.
  • the areal weight of the individual chips is typically between about 200 to 300 gsm, which correlates to prepreg layers having areal weights of about 1000 to 3500 gsm.
  • Exemplary resins that can be used to form the quasi-isotropic material include bismaleimide, polyimide, PEEK, phenolic and the like.
  • Preferred quasi-isotropic materials are a prepreg layer composed of chips made up of carbon fibers impregnated with a bismaleimide resin.
  • HexMC® Preferred quasi-isotropic materials are available from Hexcel Corporation (Dublin, Calif.) under the tradename HexMC®.
  • HexMC® is provided as an uncured prepreg in the form of sheets or layers that are laid up in the master mold and then cured according to standard procedures for bismaleimide resins.
  • HexMC® is supplied as a prepreg material that must be heat cured once the material has been placed in the master mold.
  • HexMC®/C/M61 is one type of material that is particularly preferred. This material is made from 1 ⁇ 3 ⁇ 2 inch chips of HexPLY® M65 unidirectional prepreg. Quasi-isotropic materials that have properties similar to HexMC® may be used, provided that they can be machined to the surface tolerances set forth below.
  • the mold body 11 can be machined, if desired, to obtain surface tolerances that are equivalent to metal molds.
  • a machined mold is shown in FIG. 2 at 30 .
  • the machined mold 30 is the same as mold 10 except that the original tool surfaces 12 and 13 have been machined to provide additional tool surfaces 31 , 32 , 33 , 34 and 35 .
  • the formation of these additional tool surfaces can be accomplished using any of the known machining tools and techniques that are commonly used in machining steel and/or composite material molds.
  • Such machining tools typically employ carbide and diamond coated numerical controlled (N/C) cutters.
  • a minimal amount of polishing of the tool surfaces 31 , 32 , 33 , 34 and 35 may be required after initial machining to achieve desired surface tolerances.
  • Typical surface tolerances on the order of ⁇ 0.01 inch or less can be achieved when the mold is made using the semi-isotropic material in accordance with the present invention.
  • the surface tolerances will be less than ⁇ 0.005 inch and even more preferably below ⁇ 0.003 inch.
  • machined tool surface 31 extends parallel to the mold layers so that only mold layer 24 is machined.
  • Machined tool surface 32 shows a machined surface where material is removed from mold layers 22 and 24 .
  • Machined tool surface 33 is an example of a compound surface where material is removed from a single mold layer 22 .
  • Machined tool surface 34 shows a machined surface that extends completely through two mold layers 24 and 26 .
  • Machined tool surface 35 further shows the types of possible machined surfaces that are possible when the mold body is made from quasi-isotropic material in accordance with the present invention. It should be noted that in mold 30 , mold layers 20 , 22 , 24 and 26 must be made from quasi-isotropic material since they are machined. Layers 18 and 16 are also preferably quasi-isotropic. However, these two layers ( 18 and 16 ) may be made from other compatible composite materials, if desired.
  • the machined tool surfaces are divided into five sections with different numbers in FIG. 2 for demonstrative purposes to show the various types of simple tool surfaces that can be machined into the various layers in the mold body 11 . These five sections may also be viewed as a single complex tool surface that extends four mold layers deep into the mold body.
  • the quasi-isotropic material used to form the mold bodies in accordance with the present invention allows one to make such complex machined tooling surfaces that extend through multiple mold layers and have surface tolerances on the order of those obtained with metal molds.
  • the mold body may be modified or reconditioned by adding additional mold layers to the surface of the mold body and then machining the added mold layers, if desired.
  • An exemplary modified mold is shown at 40 in FIG. 3 .
  • the modified mold 40 is the same as mold 10 except that three additional mold layers 42 , 44 and 46 have been added to the top of the mold body.
  • the phantom lines in FIG. 3 show the shape of the additional mold layers prior to machining to form the modified tool surfaces 48 , 50 and 52 .
  • the additional mold layers 42 , 44 and 46 are preferably added to the underlying mold layer 26 as pre-impregnated quasi-isotropic material (prepreg).
  • prepreg pre-impregnated quasi-isotropic material
  • a bonding agent if desired, may also be used.
  • Bismaleimide adhesives are exemplary bonding agents.
  • a master mold may be used to shape the three additional mold layers without any subsequent machining. However, as shown in FIG. 3 , it is also possible to machine the added mold layers to provide a modified or reconditioned tool surface.
  • the quasi-isotropic materials used to modify the composite molds are preferably selected from the same quasi-isotropic materials that are used to make the underlying mold body. The procedures used for applying and curing the additional layers of quasi-isotropic material are the same as those used in formation of the original mold body.
  • a mold was prepared using 11 layers of HexMC®/C/M61 BMI/carbon quasi-isotropic prepreg material.
  • the 11 layers were laid up by hand on an epoxy master mold with the use of hand pressure and a heat gun to insure that the material conformed to the mold.
  • the 11 layers of HexMC® M61 were cured at 375° F. for 240 minutes in an autoclave at 100 psi to provide the cured mold body.
  • An exemplary section of the mold is shown at 50 in FIG. 4A prior to any machining.
  • the mold ranged in thickness (t) from 0.999 inch to 0.607 inch.
  • the surface shown at 52 was the part of the mold 50 that was laid up against the master mold.
  • the surface area of the section shown at 52 is about 10 square feet.
  • the mold surface 52 was machined using a standard Carbide PVD TiAIN Ball nose cutter at a rough cut depth of approximately 1 ⁇ 4 inch using a spindle speed of 2,000 rpm and a feed rate of 60 inches per minute. The rough cut surface was then finish machined at a spindle speed of 3,000 rpm, cut depth of approximately 0.010 inch and a feed rate of 70 inches per minute to provide a finished mold 54 that has a finished mold or tool surface 56 (see FIG. 4B ). In forming the finished mold 54 , the mold surface 52 was rough cut and then machined to provide a uniform mold thickness that was approximately 0.10 inch less than the minimum thickness of the original mold 50 . The resulting finished mold 54 had thicknesses that ranged from 0.496 inch to 0.518 inch. The contour deviation of the machined mold surface 56 was less than ⁇ 0.003 inch.
  • the finished mold 54 was subjected to 114 cure (molding) cycles in an autoclave at 60 psi/350° F. over a period of approximately 855 hours (approximately 7.5 hours per cycle) without any degradation in the surface profile, surface durability or vacuum integrity of the mold.
  • the finished mold should provide up to 500 autoclave cycles at 400° F. (autoclave cycles of 10 hours or less) or 100 autoclave cycles at 450° F. (autoclave cycles of 10 hours or less).
  • molds having from 11 to 22 layers of HexMC®/C/M61 are laid up and cured as set forth above to provide void-free molds that are from 0.80 to 1.25 inch thick. These molds may be machined as described above to provide a wide variety of mold shapes that are suitable as an alternative to the steel alloy molds that are now being used to mold composite parts.
  • the molding cycles of between 7 to 10 hours for the finished mold 54 is less than the typical molding cycles for steel alloy molds, such as INVAR36. These reduced cycle times are achieved in accordance with the present invention, while still unexpectedly providing machining characteristics, surface profile tolerances and durability that typically have only been available in steel molds.
  • the composite molds of the present invention are approximately 5 times lighter than similar steel alloy molds and easier to machine.

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Moulds For Moulding Plastics Or The Like (AREA)
  • Moulding By Coating Moulds (AREA)
US11/180,831 2005-07-13 2005-07-13 Machinable composite mold Active 2027-07-04 US7510390B2 (en)

Priority Applications (11)

Application Number Priority Date Filing Date Title
US11/180,831 US7510390B2 (en) 2005-07-13 2005-07-13 Machinable composite mold
EP20060786977 EP1915245B1 (de) 2005-07-13 2006-07-11 Zerspanbare verbundform
ES06786977.6T ES2471121T3 (es) 2005-07-13 2006-07-11 Molde compuesto maquinable
PCT/US2006/027001 WO2007008953A2 (en) 2005-07-13 2006-07-11 Machinable composite mold
CN2013101996551A CN103286889A (zh) 2005-07-13 2006-07-11 可机加工的复合模具
EP14160351.4A EP2746023B1 (de) 2005-07-13 2006-07-11 Zerspanbare verbundform
CN2006800255184A CN101258012B (zh) 2005-07-13 2006-07-11 可机加工的复合模具
ES14160351.4T ES2573496T3 (es) 2005-07-13 2006-07-11 Molde compuesto maquinable
US12/400,017 US7695661B2 (en) 2005-07-13 2009-03-09 Method for molding composite structures
US12/726,677 US7972548B2 (en) 2005-07-13 2010-03-18 Method for molding composite structures
US13/118,520 US8257631B2 (en) 2005-07-13 2011-05-30 Mold for use in making composite structures

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/180,831 US7510390B2 (en) 2005-07-13 2005-07-13 Machinable composite mold

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US12/400,017 Division US7695661B2 (en) 2005-07-13 2009-03-09 Method for molding composite structures

Publications (2)

Publication Number Publication Date
US20070012858A1 US20070012858A1 (en) 2007-01-18
US7510390B2 true US7510390B2 (en) 2009-03-31

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Application Number Title Priority Date Filing Date
US11/180,831 Active 2027-07-04 US7510390B2 (en) 2005-07-13 2005-07-13 Machinable composite mold
US12/400,017 Active US7695661B2 (en) 2005-07-13 2009-03-09 Method for molding composite structures
US12/726,677 Active US7972548B2 (en) 2005-07-13 2010-03-18 Method for molding composite structures
US13/118,520 Active US8257631B2 (en) 2005-07-13 2011-05-30 Mold for use in making composite structures

Family Applications After (3)

Application Number Title Priority Date Filing Date
US12/400,017 Active US7695661B2 (en) 2005-07-13 2009-03-09 Method for molding composite structures
US12/726,677 Active US7972548B2 (en) 2005-07-13 2010-03-18 Method for molding composite structures
US13/118,520 Active US8257631B2 (en) 2005-07-13 2011-05-30 Mold for use in making composite structures

Country Status (5)

Country Link
US (4) US7510390B2 (de)
EP (2) EP2746023B1 (de)
CN (2) CN101258012B (de)
ES (2) ES2573496T3 (de)
WO (1) WO2007008953A2 (de)

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WO2012021283A1 (en) 2010-08-13 2012-02-16 Hexcel Corporation Machinable composite material
WO2013059062A2 (en) 2011-10-19 2013-04-25 Hexcel Corporation High pressure molding of composite parts
WO2013173093A1 (en) 2012-05-15 2013-11-21 Hexcel Corporation Over-molding of load-bearing composite structures
WO2016028349A2 (en) 2014-06-09 2016-02-25 Hexcel Corporation Tracers for use in compression molding of unidirectional discontinuous fiber composite molding compound
US9724854B2 (en) 2015-05-13 2017-08-08 Hexcel Composites Limited Preforms made directly from thermosetting composite chips
US10239289B2 (en) 2013-04-12 2019-03-26 Hexcel Corporation Multi-component composite structures

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US10232532B1 (en) 2006-02-02 2019-03-19 The Boeing Company Method for fabricating tapered thermoplastic composite parts
US20150129118A1 (en) * 2006-02-02 2015-05-14 The Boeing Company Compression Molding of Composite Structures Using Flexible Tooling
US8491745B2 (en) 2007-02-03 2013-07-23 The Boeing Company Method and material efficient tooling for continuous compression molding
US8691137B2 (en) 2009-03-04 2014-04-08 The Boeing Company Method of molding partus using a tool sleeve for mold die
US20070222122A1 (en) * 2006-03-23 2007-09-27 Ching-Long Ong Brightened composite sheel and method for making the same
CN102019656B (zh) * 2009-09-11 2015-03-25 固瑞特模具（太仓）有限公司 复合模具叠层板和复合模具
US10821653B2 (en) 2010-02-24 2020-11-03 Alexander M. Rubin Continuous molding of thermoplastic laminates
FR2958875B1 (fr) * 2010-04-20 2017-07-07 Snecma Dispositif de fabrication d'un carter en materiau composite et procede de fabrication mettant en oeuvre un tel dispositif
IT1410977B1 (it) * 2010-06-14 2014-10-03 Automobili Lamborghini Spa Processo e dispositivi per fabbricare prodotti in materiali compositi
ES2378682B1 (es) * 2010-06-18 2013-02-28 Airbus Operations, S.L. Método de fabricación de larguerillos con forma de "t" para un avión y herramienta de curado usada en el mismo.
US9421698B2 (en) * 2011-07-12 2016-08-23 The Boeing Company Masterless layup mandrel tool
FR2994121B1 (fr) * 2012-08-03 2015-02-06 Techni Modul Engineering Procede de fabrication d’un outillage de moulage destine au moulage d’une piece en materiau composite
US9446572B2 (en) 2012-10-31 2016-09-20 The Boeing Company Composite tool having vacuum integrity
US9817389B2 (en) * 2013-03-05 2017-11-14 Rolls-Royce Corporation Adaptively machining component surfaces and hole drilling
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US10162331B2 (en) 2015-03-02 2018-12-25 Rolls-Royce Corporation Removal of material from a surface of a dual walled component
US20170036375A1 (en) * 2015-08-07 2017-02-09 Hexcel Corporation Multi-sectional composite tooling
US9987768B2 (en) * 2016-03-31 2018-06-05 Gulfstream Aerospace Corporation Composite tools and methods for fabricating composite tools
US11123900B2 (en) * 2017-09-20 2021-09-21 Bell Helicopter Textron Inc. Mold tool with anisotropic thermal properties
JP6975618B2 (ja) * 2017-11-17 2021-12-01 三菱重工業株式会社 成形装置
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US8864070B2 (en) 2010-08-13 2014-10-21 Hexcel Corporation Machinable composite material
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US7972548B2 (en) 2011-07-05
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US20110227249A1 (en) 2011-09-22
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US8257631B2 (en) 2012-09-04
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EP2746023A1 (de) 2014-06-25
US20090165931A1 (en) 2009-07-02

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